补燃室头部距离对固冲发动机二次燃烧的影响  

Influence of Chamber Dome Length on Secondary Combustion for Solid Ducted Rocket Motor

作　　者：金秉乐 朱国强[1] 李进贤[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《兵器装备工程学报》2016年第5期57-60,共4页Journal of Ordnance Equipment Engineering

基　　金：中央高校基本科研业务费西北工业大学科研基地平台建设基金(3102014KYJD006)

摘　　要：补燃室头部距离是影响固体火箭冲压发动机二次燃烧效率的关键参数,采用数值模拟的方法研究分析了该参数对固体火箭冲压发动机二次燃烧效率的影响,数值结果与同等条件下实验结果的对比分析表明:补燃室头部距离的增大,可增大头部的漩涡区,从而使固相颗粒在补燃室头部的驻留时间得以延长,这对固相颗粒的点火燃烧十分有利,但对提高整个补燃室掺混燃烧效率的作用有限,因此补燃室长度一定的情况下,存在一个最佳的头部距离。The dome length of afterburning chamber of solid rocket ramjet is the key parameter of the secondary combustion efficiency. The influence of the parameters of solid rocket ramjet on the secondary combustion efficiency was analyzed and studied by adopting the method of numerical simulation. The numerical results and the experimental results show that incresing the dome length can increse the vortex area of the dome, so that to extend the residence time of solid phased particles in afterburning chamber, which is benefit to the ignition burning of solid phased particles, but it is limited in improving the combustion efficiency of the whole afterburning chamber. Thus, there exists a best dome length under the condition of certain afterburning chamber length.

关 键 词：固火箭冲压发动机 头部距离 二次燃烧 数值模拟 

分 类 号：TJ013[兵器科学与技术—兵器发射理论与技术] V430[航空宇航科学与技术—航空宇航推进理论与工程]